Recombination Losses in Rocket Nozzles With Storable Propellants

Koppang, R.; Simkin, D. J.

doi:10.2514/3.2012

Cited by 3 publications

(1 citation statement)

References 4 publications

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“…The endothermic dissociation reactions producing the atoms and free radicals would reduce the combustion temperature for this reaction to an equilibrium temperature of 3045' K. The simulation of the storable- propellant Composition therefore must provide re@tante that produce the variety of products shown in equation (2). Theae products of combustion contain M)…”

Section: Compositionmentioning

confidence: 99%

Combustion of hydrogen and methane to simulate expansion of storablepropellants

Friedman

Gaugler²,

Lezberg³

1968

4th Propulsion Joint Specialist Conference

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An experimental investigation of exhaust-nozzle temperatures for the storable aystem, 50 percent UDMH-50 percent hydrazine/nitrogen tetroxide, was conducted using hydrogen and methane fuel burned in oxygen-enriched air to provide the s'ame atomic constituents as the storable propellants. Oxidant-fuel mass ratios of 1.6 to 2.5 at 3.7 atmospheres combustionchamber pressure were simulated by control of the fuel. oxygeh, and ai< flows; inlet enthalpies were duplicated by preheating the oxidant in a pebble-bed storage heater. Static temperatures, measured by a spectral line reversal pyrometer at 5 stations in the expanding portion of a 5.5-area-ratio, Mach 3 nozzle, were found ta be nearly insensitive to oxidat-fuel ratio and close to temperatures calculated for a frozen expansion. This study demonstrated the feasibility of the simulation technique for exhaust-nozzle kinetic studies. Results agreed well with a simplified kinetic analysis based on a I'sudden freezing" of the nozzle recombination reactions at an area ratio of 1.04 upstream of the throat. c.

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Section: Compositionmentioning

confidence: 99%